夹层板大挠度问题的力学表征与数值模拟  

Mechanical performance and numerical simulation of sandwich plate with large deflection

作　　者：李伟[1] 靳诚忠[1] 刘思远[1] 

机构地区：[1]沈阳飞机设计研究所综合强度部,沈阳110035

出　　处：《沈阳航空航天大学学报》2014年第1期24-27,共4页Journal of Shenyang Aerospace University

摘　　要：随着材料制备工艺的发展和成型加工技术的日趋完善,夹层板在现代航空领域结构设计中获得了广泛应用,以获得理想的重量及其它功能性指标,工程分析时往往利用薄板理论进行近似分析,这忽略了夹层板的良好的抗弯特性,给分析结果带来较大误差。在薄板大挠度问题及夹层板相关理论的基础上,提出分段叠加法分析大挠度夹层板的变形机理,并利用有限元进行了数值模拟,结合某型飞机蜂窝轮舱壁板静力试验验证了夹层板大挠度变形机理的合理性,证明了叠加法的有效性。With the development of material manufacturing techniques and the gradual perfection of contour processing technology, sandwich plates have been widely used in modem aircraft structure design to obtain i- deal weight and other functional indicators. The thin plate theory is often used in engineering approximate a- nalysis, which ignores the good bending characteristics of sandwich plates and brings large errors to the ana- lytical results. Based on the large deflection problem of thin plates and related theories of sandwich plates, the method of subsection superposition is proposed to analyze the deformation mechanism of the large de- flection of sandwich plates, which is simulated numerically by finite element. Combining the static test of certain type of aircraft honeycomb sandwich compartment panel, the paper verifies the rationality of deforma- tion mechanism and proves the effectiveness of the superposition method.

关 键 词：飞行器设计 夹层板 大挠度 分段叠加法 

分 类 号：O342[理学—固体力学] V215.5[理学—力学]